CN1303990A - Moving vane of turbine - Google Patents
Moving vane of turbine Download PDFInfo
- Publication number
- CN1303990A CN1303990A CN00135368.3A CN00135368A CN1303990A CN 1303990 A CN1303990 A CN 1303990A CN 00135368 A CN00135368 A CN 00135368A CN 1303990 A CN1303990 A CN 1303990A
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- Prior art keywords
- turbine
- moving vane
- stator blade
- surface portion
- leading edge
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- 239000012530 fluid Substances 0.000 claims description 10
- 230000000694 effects Effects 0.000 claims description 8
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- NCGICGYLBXGBGN-UHFFFAOYSA-N 3-morpholin-4-yl-1-oxa-3-azonia-2-azanidacyclopent-3-en-5-imine;hydrochloride Chemical compound Cl.[N-]1OC(=N)C=[N+]1N1CCOCC1 NCGICGYLBXGBGN-UHFFFAOYSA-N 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/02—Formulas of curves
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a moving turbine blade. When an angle, which a tangent to a dorsal surface portion at a front edge of the moving turbine blade makes with a straight line perpendicular to a rotating shaft of a turbine, is designated as theta, and a geometrical outlet angle of a stationary blade is designated as alphan, theta is in the relationship alphaN+2 DEG <theta<alphaN+12 DEG. As a result, the shape of the dorsal surface portion, at the front edge and in a portion adjacent thereto, of the moving turbine blade is not parallel to a stationary blade wake. Thus, the moving turbine blade can contribute to increasing the efficiency of the turbine, while suppressing an unsteady sharp increase in flow velocity.
Description
The present invention relates to a kind of moving vane of turbine, particularly a kind of moving vane of turbine that is used for axial flow impulse turbine machine (anaxial flow impulse turbine).
Fig. 5 represents is according to the moving vane of turbine of the axial flow impulse turbine machine of the prior art structural drawing together with the turbine engine stator blade.As shown in the figure, a plurality of moving vane of turbine 1 are set on the circumferencial direction of turbine engine impeller (not shown), and a plurality of stator blades 2 is installed on the casing (not shown) of axial flow impulse turbine machine.Stator blade 2 plays the effect of nozzle, so that high speed, high-pressure liquid (for example steam) to be provided to moving vane of turbine 1.
Show the generation of an important phenomenon for the analysis of flowing velocity in this axial flow impulse turbine machine.With regard to such turbine engine, traditional technology is thought always: with the low flow velocity zone that belt-like form extends, promptly so-called stator blade wake flow (wake) 3 (part of adding some points in the drawings) forms at the rear of the trailing edge 2a of stator blade 2.And nearest discovery is: when moving vane of turbine was cut stator blade wake flow 3, the high-speed region 4 of hurried accelerating fluid (being decorated with cross-hatched part among the figure) will form on the 1a of back surface portion of moving vane of turbine 1 when turbine engine rotates.It is as follows to form this regional mechanism: the wake flow 3 of stator blade plays the effect of effective " wall ", has hindered the master stream with high flow rate.As a result, when making the wake flow 3 of moving vane of turbine 1 close stator blade, between stator blade wake flow 3 and moving vane of turbine 1, formed the aditus laryngis of a passage effectively when rotating (direction of rotational motion is represented with arrow A in the drawings) by moving vane of turbine 1.As a result, through certain hour, will on the 1a of back surface portion of moving vane of turbine 1, form the high-speed region 4 of hurried accelerating fluid.And stator blade wake flow 3 is to form in the back of each stator blade 2, and also all produces a high-speed region 4 corresponding to each stator blade wake flow 3.But, only shown that in the accompanying drawings a stator blade wake flow 3 and a high-speed region 4 illustrate as representative.
When approaching stator blade wake flow 3 take place in a flash to form on the 1a of back surface portion of the hurried above-mentioned unsteady state high-speed region 4 that increases of liquid speed at moving vane of turbine 1 time, be very big in the loss of the turbine at this place.This be because: if there is a wall to get lodged on the passage of fluid, then is accompanied by high-speed region and produces friction, and the kinetic energy of fluid can promptly can produce total loss of pressure head owing to this friction changes heat energy into the different of low-speed region flow velocity.The efficient of turbine engine will descend like this.
The present invention finishes at the problems referred to above on the basis of existing technology.Purpose of the present invention just provides a kind of moving vane of turbine, and this blade can help to improve the efficient of turbine engine, and suppresses the hurried rising of unsteady state of flow velocity.
In order to realize above-mentioned target, the inventor studies the condition that forms obvious high-speed region 4, and has obtained following discovery: the shape of stator blade wake flow 3 only is by the decision of the shape of stator blade 2.On the other hand, thus the exit angle that flows out from stator blade 2 based on fluid, the shape of guaranteeing to determine to velocity flow profile stable its trailing edge 1d moving vane of turbine 1 from the leading edge 1b of moving vane of turbine 1.In view of the above, just can roughly determine the general shape of entrance angle and the 1a of back surface portion, the 1c of ventral surface portion.As a result, with regard to the moving vane of turbine 1 of prior art, moving vane of turbine 1 just is processed to parallel with stator blade wake flow 3 in the shape of the 1a of back surface portion at leading edge 1b place.The shape of the 1a of back surface portion of this moving vane of turbine 1 that is parallel to stator blade wake flow 3 may be the main cause that causes flow velocity instability and the hurried increase of flow velocity.When the 1a of back surface portion is processed to be parallel to stator blade wake flow 3, between the 1a of back surface portion of stator blade wake flow 3 and moving vane of turbine 1, a passage aditus laryngis or narrow orifice have been formed significantly.
Based on above-mentioned discovery, characteristics of the present invention can be by following 1) to 5) bar illustrated:
1) a plurality of moving vane of turbine are along the circumferential directions of impeller, and moving vane of turbine is subjected to leaving the effect as the fluid of the stator blade of stator blade, and rotating force is passed to impeller, wherein:
Moving vane of turbine is cut sth. askew in leading edge with the back surface portion in the part of adjacent leading edge, so that it does not parallel with the stator blade wake flow.
According to above-mentioned situation of the present invention, can remove (displaced) from the stator blade wake flow in the shape of the back surface portion of moving vane of turbine leading edge.Like this in turbine engine rotation when the stator blade wake flow is crossed in the moving vane of turbine crosscut, just can make the channel widens that forms between the back surface portion of moving vane of turbine leading edge and the stator blade wake flow.Thereby the instability increase of the flow velocity in back surface portion just can be suppressed.Therefore,, also can eliminate the high-speed region of the flow velocity of part, reduce total head loss herein, thereby help improving the efficient of turbine engine even when making moving vane of turbine periodically the stator blade wake flow is crossed in crosscut with the motion of moving vane of turbine.
2) the in the above the 1st) in the described moving vane of turbine of bar, be defined as θ when the tangent line of the back surface portion at moving vane of turbine leading edge place with the perpendicular angle that straight line constituted of the running shaft of turbine engine, and how much exit angles of stator blade are defined as α
NThe time, then there is following relation in θ:
α
N+2°＜θ＜α
N+12°
In view of the above, not only the 1st) effect described in the bar realizes, and the CLV ceiling limit value at θ angle also limited.Like this, the geometrical relationship such as the moving vane of turbine relevant with stator blade exit angle inlet angle etc. also can both guarantee the best.Thus, moving vane of turbine can improve the efficient of turbine engine, and don't sacrifices other performance.
3) the in the above the 1st) or 2) in the described moving vane of turbine of bar, when the maximum ga(u)ge of moving vane of turbine is defined as T
Max, and width of blade, promptly rotate the distance between turbine blade leading edge and the trailing edge, be defined as W, then T
Max/ W satisfies following relation:
0.33＜T
max/W＜0.42
In view of the above, not only the 1st) and the 2nd described effect be achieved, and the blade shape of moving vane of turbine also is a thin-walled shape.Like this, the passage between the adjacent moving vane of turbine has just broadened.Mean velocity herein just can descend.As a result, the high-flow area between the back surface portion of stator blade wake flow and moving vane of turbine just can further be removed effectively, and further promotes the raising of turbine engine efficient.
4) the in the above the 1st) or 2) in the described moving vane of turbine of bar, when the tangent line of the ventral surface portion at moving vane of turbine leading edge place and the angle that tangent line constituted of back surface portion are defined as β
IncThe time, β then
IncThere is following relation:
13°＜β
inc＜27°
In view of the above, not only the 1st) and the effect described in the 2nd be implemented, and very thin at the leading edge vicinity vane thickness that flow velocity is especially significantly increased because of the stator blade wake flow of moving vane of turbine.Channel widens between the adjacent like this moving vane of turbine, then mean velocity herein descends.As a result, the high-flow area between the back surface portion of stator blade wake flow and moving vane of turbine just can further be removed effectively, and can further promote the raising of turbine engine efficient.
5) the in the above the 1st) or 2) in the described moving vane of turbine of bar, when the maximum ga(u)ge of moving vane of turbine is defined as T
Max, and width of blade, promptly rotate the distance between turbine blade leading edge and the trailing edge, be defined as W, then T
Max/ W satisfies following relation:
0.33＜T
Max/ W＜0.42, and:
When the tangent line of the ventral surface portion at moving vane of turbine leading edge place and the angle that tangent line constituted of its back surface portion are defined as β
IncThe time, β then
IncSatisfy following relation:
13°＜β
inc＜27°
In view of the above, the 1st) or 2) and 3) and 4) aspect described in institute produce effect and all be implemented.Therefore, the raising of turbine engine efficient is very remarkable.
By detailed description, the present invention is understood more fully below in conjunction with accompanying drawing.But above-mentioned explanation only is illustrative, the present invention is not construed as limiting.In the accompanying drawing:
Figure 1A is the view of the relevant embodiment of the invention to Fig. 1 C.Wherein, Figure 1A is the schematic representation of expression moving vane of turbine, and Figure 1B summary shows the zoomed-in view of how much exit angles of stator blade, and Fig. 1 C is the partial view that the leading edge of moving vane of turbine is shown;
Fig. 2 is shape (solid line part) schematic representation of expression according to two moving vane of turbine of the embodiment of the invention, and what compare with it is shape (dotted portion) according to two moving vane of turbine of prior art;
Fig. 3 is the performance diagram of expression according to the blade surface flowing velocity distribution characteristic (solid line part) of the moving vane of turbine of the embodiment of the invention, and what compare with it is blade fluid velocity distribution characteristic (dotted portion) curve according to the moving vane of turbine of prior art;
What Fig. 4 represented is turbine engine temperature efficiency (the turbine temperature efficiency) performance diagram (solid line part) that has according to the moving vane of turbine of the embodiment of the invention, and what compare with it is temperature efficiency (dotted portion) curve that has according to the turbine engine of the moving vane of turbine of prior art;
Fig. 5 is according to the moving vane of turbine of the axial flow impulse turbine machine of the prior art schematic representation together with stator blade.
Referring now to accompanying drawing embodiments of the invention are illustrated, but be noted that the present invention is not limited thereto.
Present embodiment relates to an invention, and this invention is to develop for the back surface portion shape specialized designs of the moving vane of turbine relevant with the stator blade wake flow.Problem is should set which type of moving vane angle corresponding to the angle of the wake flow of stator blade.For this reason, how much exit angle α
NBe defined as the exit angle corresponding parameter with stator blade, and with respect to this how much exit angle α
N, specifically determine preferred moving vane of turbine shape.Stator blade 2 is with shown in Figure 5 of the prior art just the same.Below, will present embodiment be described in conjunction with stator blade 2 and moving vane of turbine.
Figure 1A relates to the view of the embodiment of the invention to Fig. 1 C, wherein, Figure 1A is the schematic representation of expression moving vane of turbine, and Figure 1B is the zoomed-in view that a summary is represented stator blade how much exit angles, and Fig. 1 C is the partial view of the front edge of the moving vane of turbine that extracts.
In Figure 1A, what reference character 11 was represented is moving vane of turbine, and what 11a represented is its back surface portion, and 11b is a leading edge, and 11c is a ventral surface portion, and 11d is a trailing edge.A plurality of this moving vane of turbine are installed on the corresponding position shown in Figure 5, and promptly they are installed in the circumferencial direction of turbine engine impeller (not shown) and relative with stator blade 2.The fluid that flows out from stator blade 2 will act on the moving vane of turbine 11 like this, and turning effort power is passed to the turbine engine impeller.At this moment, by tangent line L at the 11a of back surface portion of the leading edge 11b of moving vane of turbine 11
1Be defined as θ with the angle that is constituted with the perpendicular straight line L2 of turbine engine running shaft, and how much exit angles of stator blade 2 are defined as α
N, then θ is limited in the scope of being determined by following representation (1):
α
N+2°＜θ＜α
N+12° (1)
More preferably, θ is in by in following representation (2) the institute restricted portion:
α
N+5°＜θ＜α
N+7° (2)
Here, how much exit angle α of stator blade 2
NDetermine by following method: shown in Figure 1B, the stator blade spacing, the distance between the promptly adjacent stator blade 2 is defined as C
N, and stator blade aditus laryngis width, promptly one trailing edge 2a from adjacent stator blade 2 is defined as δ to the distance of the back surface portion of another stator blade 2
NAt this moment, α
NThen by equation α
N=sin
-1(δ
N/ C
N) provide, because given stator blade aditus laryngis width δ
NStraight line and given how much exit angle α
NThe tangent line of stator blade 2 can regard orthogonal approx as.
The above-mentioned quantitative upper limit to the θ angle is definite considering following factor: how much exit angle α that promptly work as stator blade 2
NDetermined that then the preferable shape at the leading edge 11b place of moving vane of turbine 11 is also just determined (corresponding with it).This preferable shape is provided by θ ' angle and above-mentioned θ angle sum, here θ ' angle be moving vane of turbine 11 leading edge 11b place the 11c of ventral surface portion tangent line L3 with perpendicular to the straight line L of turbine engine running shaft
2The angle that is constituted.Like this, when θ angle fixedly the time, θ ' angle is then determined in the summation framework at θ ' and θ angle.That is to say that this angle can not exceed the scope corresponding with this summation.
The restriction that θ is carried out as described above, the shape that is positioned at the 11a of back surface portion of moving vane of turbine 11 leading edge 11b just can be removed from the wake flow 3 (see Fig. 5, the following description also is like this) of stator blade.In other words, the shape of the 11a of back surface portion and the wake flow of stator blade 3 are parallel no longer just, thereby in the turbine engine rotary course when stator blade wake flow 3 is crossed in the moving vane of turbine crosscut, passage between the 11a of back surface portion that makes at moving vane of turbine 11 leading edge 11b and the wake flow 3 of stator blade can broaden, and then makes that the astable increase of flow velocity is suppressed in back surface portion.
What Fig. 2 represented is shape (solid line part) schematic representation of the moving vane of turbine 11 of the above embodiments according to the present invention, and what compare with it is shape (dotted portion) according to the moving vane of turbine 1 of prior art shown in Figure 5.Will see too clearly with reference to accompanying drawing, what adopt according to the moving vane of turbine 11 of present embodiment is by (chamfering) shape of formation afterwards of cutting sth. askew of the 1a of back surface portion with close the leading edge 1b of the moving vane of turbine 1 of prior art (see Fig. 5, the explanation of back also is like this).Therefore, the shape of the 11a of back surface portion can offset the direction of stator blade wake flow.Point out in passing, for moving vane of turbine 1 according to prior art, the θ angle of formation almost with how much exit angle α of stator blade 2
NIdentical, the θ angle is no more than (α at least
N+ 2 °).
Because the front is to the numerical limit at θ angle, the shape of the 11a of back surface portion of moving vane of turbine 11 just can be removed the wake flow 3 of stator blade, rather than is parallel to the wake flow 3 of stator blade.In the present embodiment, also adopt more following additional quantitative restrictions:
Shown in Figure 1A, the diameter of a circle of the shape of being represented by double dot dash line that is inscribed within moving vane of turbine 11 is being represented the thickness of relevant position place moving vane of turbine 11.When the maximum ga(u)ge of moving vane of turbine 11 is defined as T
Max, and the width of blade (being the leading edge 11b of moving vane of turbine 11 and the distance between the trailing edge 11d) is defined as W, then T
MaxThe ratio of/W should satisfy following relationship: 0.33＜T
Max/ W＜0.42, preferably 0.34＜T
Max/ W＜0.38.Because this conditional request, the blade shape of moving vane of turbine 11 is thin-walleds.Like this, the channel widens between the adjacent moving vane of turbine 11, thus the mean velocity at this place is minimized.Point out in passing, according to the T of the moving vane of turbine 1 of prior art
MaxThe ratio of/W is greater than 0.42.
In the present embodiment, also to carry out following quantitative restriction: shown in Fig. 1 C, the tangent line L of the 11a of back surface portion of moving vane of turbine 11 leading edge 11b
4Tangent line L with the 11c of its ventral surface portion
5The angle that is constituted is defined as β
Inc, β then is set
IncTo satisfy relation down: 13 °＜β
Inc＜27 °.Because this conditional request, moving vane of turbine 11 diminishes at the vane thickness of flow velocity because of the leading edge 11b vicinity of stator blade wake flow 3 hurried increases, the channel widens between the adjacent like this moving vane of turbine 11, thus be reduced at the mean velocity at this place.Point out in passing, according to the β of the moving vane of turbine 1 of prior art
IncThe angle is greater than 27 °.
Determine T
Max/ W ratio and β
IncThe vane thickness of the lower limit at angle to obtain being scheduled to, because the vane thickness of moving vane of turbine 11 is subjected to the certain condition constraint, the purpose of this constraint is to form steady velocity flow profile at the leading edge 11b of moving vane of turbine 11 in the passage of trailing edge 11d.
In the turbine engine that has according to the moving vane of turbine 11 of above-mentioned present embodiment of the present invention, the shape of the 11a of back surface portion of moving vane of turbine 11 is not parallel with the wake flow of stator blade 3 mutually.Like this, under the situation of moving vane of turbine 11 rotation,, also can between the wake flow 3 of stator blade and moving vane of turbine 11, guarantee relatively large passage even when the wake flow 3 of stator blade is crossed in moving vane of turbine 11 crosscuts.Thereby, in this passage area, can not form high-speed region 4 (see figure 5)s of the hurried increase of flow velocity.Go back reduced value T in addition
Max/ W and β
IncThe angle is optimized, to reduce the mean velocity between the adjacent moving vane of turbine 11.Measure has prevented the formation of high-speed region 4 and so on.
Fig. 3 shows the characteristic curve according to the blade surface liquid speed distribution character (solid line part) of the moving vane of turbine of the embodiment of the invention, and what compare with it is blade fluid velocity distribution characteristic (dotted portion) curve according to the moving vane of turbine of prior art.Fig. 4 shows the temperature efficiency characteristic curve (solid line part) that has according to the turbine engine of the moving vane of turbine 11 of the foregoing description, and what compare with it is temperature efficiency (dotted portion) curve that has according to the turbine engine of the moving vane of turbine of prior art.With reference to Fig. 3, we as can be seen, flow velocity obviously descends near the 11a of back surface portion the moving vane of turbine 11 leading edge 11b.With reference to Fig. 4, engrave all during turbine engine efficient any in one-period undoubtedly and improved, and the average efficiency of one-period obviously increases.One-period among Fig. 4 is: from the moment of a moving vane of turbine 11 crosscut stator blade wake flows 3, and this section period till the moment of the next stator blade wake flow 3 of next moving vane of turbine 11 crosscuts.To being described in detail as follows of Fig. 3 and Fig. 4: angle θ=21.9 °, ratio T
Max/ W=0.38, angle β
Inc=24.3 °.
Moving vane of turbine in the above-described embodiment is that the moving vane as the impulse turbine machine is described, but is not limited only to this.But for having less inlet angle and having the impulse turbine machine that its shape is tending towards the back surface portion that parallels with the stator blade wake flow, this moving vane of turbine is effective especially.
Although describe the present invention, be noted that the present invention is not limited thereto, but can change in many other modes with aforesaid method.These are changed and are not construed to is to depart from the spirit and scope of the invention, and these changes all are conspicuous for one of ordinary skill in the art, and all will comprise in the appended claims.
Claims (5)
1. moving vane of turbine, the moving vane of turbine that a plurality of circumferential directions along impeller are arranged in turbine engine, this moving vane of turbine is subjected to the effect of the fluid that leaves from the stator blade as stator blade and rotating force is delivered on the turbine engine impeller, wherein:
Moving vane of turbine is cut sth. askew at the leading edge place and with the shape of back surface portion in the part of adjacent leading edge, thereby can not parallel with the stator blade wake flow.
2. the described moving vane of turbine of claim 1, it is characterized in that, when being defined as θ at the tangent line of moving vane of turbine leading edge place back surface portion with the perpendicular angle that straight line constituted of turbine engine running shaft, and how much exit angles of stator blade are defined as α
NThe time, then there is following relation in θ:
α
N+2°＜θ＜α
N+12°
3. claim 1 or 2 described moving vane of turbine is characterized in that:
When the maximum ga(u)ge of moving vane of turbine is defined as T
Max, and width of blade, that is the distance between moving vane of turbine leading edge and the trailing edge, be defined as W, then T
MaxThere is following relation in/W:
0.33＜T
max/W＜0.42
4. claim 1 or 2 described moving vane of turbine is characterized in that:
When the tangent line of the ventral surface portion at moving vane of turbine leading edge place and the angle that tangent line constituted of back surface portion are defined as β
IncThe time, β then
IncThere is following relation:
13°＜β
inc＜27°
5. claim 1 or 2 described moving vane of turbine is characterized in that:
When the maximum ga(u)ge of moving vane of turbine is defined as T
Max, and width of blade, promptly the distance between moving vane of turbine leading edge and the trailing edge is defined as W, then T
MaxThere is following relation in/W:
0.33＜T
Max/ W＜0.42 and:
When the tangent line of the ventral surface portion at moving vane of turbine leading edge place and the angle that tangent line constituted of back surface portion are defined as β
IncThe time, β then
IncThere is following relation:
13°＜β
inc＜27°
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3260/00 | 2000-01-12 | ||
| JP2000003260A JP3785013B2 (en) | 2000-01-12 | 2000-01-12 | Turbine blade |
| JP3260/2000 | 2000-01-12 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1303990A true CN1303990A (en) | 2001-07-18 |
| CN1276169C CN1276169C (en) | 2006-09-20 |
Family
ID=18532235
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN00135368.3A Expired - Lifetime CN1276169C (en) | 2000-01-12 | 2000-12-13 | Moving vane of turbine |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US6533545B1 (en) |
| JP (1) | JP3785013B2 (en) |
| CN (1) | CN1276169C (en) |
| ES (1) | ES2172439B2 (en) |
| MX (1) | MXPA01000038A (en) |
| MY (1) | MY126074A (en) |
| SG (1) | SG85218A1 (en) |
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| CN103590861A (en) * | 2012-08-15 | 2014-02-19 | 广东核电合营有限公司 | High-pressure cylinder of steam turbine for nuclear power station and design method thereof |
| CN106570237A (en) * | 2016-10-25 | 2017-04-19 | 浙江理工大学 | Method and system for monitoring stator blade thickness of turbine of blast furnace gas waste heat recovery device |
| WO2020237850A1 (en) * | 2019-05-27 | 2020-12-03 | 合肥工业大学 | Bionic airfoil blade |
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| US7216694B2 (en) * | 2004-01-23 | 2007-05-15 | United Technologies Corporation | Apparatus and method for reducing operating stress in a turbine blade and the like |
| KR100713252B1 (en) * | 2005-07-08 | 2007-05-02 | 부산대학교 산학협력단 | Rotor blade for axial-flow turbine |
| DE102008031781B4 (en) * | 2008-07-04 | 2020-06-10 | Man Energy Solutions Se | Blade grille for a turbomachine and turbomachine with such a blade grille |
| DE102014004745A1 (en) * | 2014-04-01 | 2015-10-01 | Daimler Ag | Turbine wheel for a turbine, in particular an exhaust gas turbocharger |
| US10508549B2 (en) * | 2014-06-06 | 2019-12-17 | United Technologies Corporation | Gas turbine engine airfoil with large thickness properties |
| CN105888984B (en) * | 2014-12-29 | 2019-02-05 | 上海适科暖通机电设备科技有限公司 | A kind of differential pressure type wind speed transducer |
| US11059018B2 (en) * | 2018-05-16 | 2021-07-13 | Dresser-Rand Company | Turbomachine chemical reactor and method for cracking hydrocarbons in a process fluid |
| CN108799199B (en) * | 2018-05-29 | 2020-01-10 | 中国航空发动机研究院 | Design method of high-load wide-margin camber-adjustable tandem cascade |
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| JPS5765802A (en) * | 1980-10-06 | 1982-04-21 | Mitsubishi Heavy Ind Ltd | Fluid turbine |
| US4431376A (en) * | 1980-10-27 | 1984-02-14 | United Technologies Corporation | Airfoil shape for arrays of airfoils |
| US4968216A (en) * | 1984-10-12 | 1990-11-06 | The Boeing Company | Two-stage fluid driven turbine |
| US5277549A (en) * | 1992-03-16 | 1994-01-11 | Westinghouse Electric Corp. | Controlled reaction L-2R steam turbine blade |
| KR950007521B1 (en) * | 1992-08-14 | 1995-07-11 | 엘지전자주식회사 | Siroco fan |
| DE4228879A1 (en) * | 1992-08-29 | 1994-03-03 | Asea Brown Boveri | Turbine with axial flow |
| US5486091A (en) * | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
| JP3621216B2 (en) * | 1996-12-05 | 2005-02-16 | 株式会社東芝 | Turbine nozzle |
-
2000
- 2000-01-12 JP JP2000003260A patent/JP3785013B2/en not_active Expired - Lifetime
- 2000-11-03 SG SG200006384A patent/SG85218A1/en unknown
- 2000-11-03 ES ES200002649A patent/ES2172439B2/en not_active Expired - Fee Related
- 2000-11-09 US US09/708,664 patent/US6533545B1/en not_active Expired - Lifetime
- 2000-12-13 CN CN00135368.3A patent/CN1276169C/en not_active Expired - Lifetime
-
2001
- 2001-01-08 MX MXPA01000038A patent/MXPA01000038A/en active IP Right Grant
- 2001-01-10 MY MYPI20010078A patent/MY126074A/en unknown
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103590861A (en) * | 2012-08-15 | 2014-02-19 | 广东核电合营有限公司 | High-pressure cylinder of steam turbine for nuclear power station and design method thereof |
| CN103590861B (en) * | 2012-08-15 | 2015-11-18 | 广东核电合营有限公司 | The high-pressure cylinder of steam turbine for nuclear power station and design method thereof |
| CN106570237A (en) * | 2016-10-25 | 2017-04-19 | 浙江理工大学 | Method and system for monitoring stator blade thickness of turbine of blast furnace gas waste heat recovery device |
| CN106570237B (en) * | 2016-10-25 | 2020-03-17 | 浙江理工大学 | Turbine stator blade thickness monitoring method and system of blast furnace gas waste heat recovery device |
| WO2020237850A1 (en) * | 2019-05-27 | 2020-12-03 | 合肥工业大学 | Bionic airfoil blade |
Also Published As
| Publication number | Publication date |
|---|---|
| ES2172439A1 (en) | 2002-09-16 |
| MY126074A (en) | 2006-09-29 |
| JP2001193403A (en) | 2001-07-17 |
| JP3785013B2 (en) | 2006-06-14 |
| US6533545B1 (en) | 2003-03-18 |
| CN1276169C (en) | 2006-09-20 |
| MXPA01000038A (en) | 2002-08-06 |
| SG85218A1 (en) | 2001-12-19 |
| ES2172439B2 (en) | 2004-04-01 |
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